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公开(公告)号：US20140062032A1
公开(公告)日：2014-03-06
申请号：US13690541
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Edward Wolfe , Victor John Morgan , Neelesh Nandkumar Sarawate , David Wayne Weber
IPC: F01D11/00
CPC classification number: F01D11/005 , F05D2240/57 , F16J15/128
Abstract: A seal assembly is provided. The seal assembly includes a first outer shim and a second outer shim The second outer shim is operably coupled to the first outer shim and comprises at least one substantially impermeable portion that spans across a gap between at least two turbomachine components. The second outer shim further engages the at least two turbomachine components to substantially seal the gap. The substantially impermeable portion is substantially planar at least along a width of the seal assembly. The seal assembly further includes a resilient member that is either coupled to at least a portion of an outer surface of the first outer shim or comprises an integral portion of the first outer shim The resilient member engages the seal assembly to contact bottom surfaces of a cavity defined between the at least two turbomachine components.
Abstract translation: 提供密封组件。 密封组件包括第一外垫片和第二外垫片第二外垫片可操作地联接到第一外垫片，并且包括穿过至少两个涡轮机构件之间的间隙的至少一个基本不可渗透部分。 第二外垫片进一步接合至少两个涡轮机组件以基本上密封间隙。 至少沿着密封组件的宽度，基本上不可渗透部分基本上是平面的。 密封组件还包括弹性构件，其被联接到第一外垫片的外表面的至少一部分，或包括第一外垫片的整体部分。弹性构件接合密封组件以接触空腔的底表面 限定在所述至少两个涡轮机组件之间。
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公开(公告)号：US11732593B2
公开(公告)日：2023-08-22
申请号：US17519038
申请日：2021-11-04
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/60
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US20220056805A1
公开(公告)日：2022-02-24
申请号：US17519038
申请日：2021-11-04
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10450950B2
公开(公告)日：2019-10-22
申请号：US15334448
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber
Abstract: A turbomachine blade according to various embodiments includes: a body having: a leading edge; a trailing edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side; a root; and a tip opposing the root; and a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including: a first section extending from the root toward the tip along the pressure side; a second section extending from the first section toward the trailing edge; and a third section extending from the trailing edge along the suction side, wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge.
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公开(公告)号：US10301946B2
公开(公告)日：2019-05-28
申请号：US15334517
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
Abstract: A turbine blade airfoil including various internal cavities that are fluidly coupled is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil. The first pressure side cavity may receive a coolant. The airfoil may also include a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, and at least one channel positioned between and fluidly coupling the first and second pressure side cavities. The channel may be positioned radially between a top surface and a bottom surface of the first and second pressure side cavities. Additionally, the airfoil may include a trailing edge cooling system positioned adjacent a trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may receive a portion of the coolant from the first pressure side cavity.
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Patent Agency Ranking
公开(公告)号：US10208608B2
公开(公告)日：2019-02-19
申请号：US15239968
申请日：2016-08-18
Applicant: General Electric Company
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.
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公开(公告)号：US10190421B2
公开(公告)日：2019-01-29
申请号：US15019487
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Neil Ristau , Zachary James Taylor , David Wayne Weber
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.
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公开(公告)号：US10053990B2
公开(公告)日：2018-08-21
申请号：US15152707
申请日：2016-05-12
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II
CPC classification number: F01D5/187 , F01D5/141 , F01D5/147 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2250/14 , F05D2250/185 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
Abstract: An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.
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公开(公告)号：US10052683B2
公开(公告)日：2018-08-21
申请号：US14977028
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , David Wayne Weber , Michelle Jessica Iduate , Brendon James Leary , Joseph Anthony Weber
CPC classification number: B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C21/14 , F01D5/187 , F05D2220/32 , F05D2230/21 , F05D2260/20 , G01B17/02 , G01B21/08
Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.
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公开(公告)号：US20180112533A1
公开(公告)日：2018-04-26
申请号：US15334448
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber
CPC classification number: F02C3/04 , F01D5/187 , F05D2220/32 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/202
Abstract: A turbomachine blade according to various embodiments includes: a body having: a leading edge; a trailing edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side; a root; and a tip opposing the root; and a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including: a first section extending from the root toward the tip along the pressure side; a second section extending from the first section toward the trailing edge; and a third section extending from the trailing edge along the suction side, wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge.
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